Aerodynamic characteristics of a free-flight scramjet vehicle in shock tunnel
Marie Tanno,Hideyuki Tanno +1 more
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TLDR
In this paper, a multi-component aerodynamic test for an airframe-engine integrated scramjet vehicle model was conducted in the free-piston shock tunnel HIEST, where a new method using multiple piezoelectric accelerometers was developed based on overdetermined system analysis.Abstract:
A multi-component aerodynamic test for an airframe-engine integrated scramjet vehicle model was conducted in the free-piston shock tunnel HIEST. A free-flight force measurement technique was applied to the scramjet vehicle model named MoDKI. A new method using multiple piezoelectric accelerometers was developed based on overdetermined system analysis. Its unique features are the following: (1) The accelerometer’s mounting location can be more flexible. (2) The measurement precision is predicted to be improved by increasing the number of accelerometers. (3) The angular acceleration can be obtained with single-axis translational accelerometers instead of gyroscopes. (4) Through the averaging process of the multiple accelerometers, model natural vibration is expected to be mitigated. With eight model-onboard single-axis accelerometers, the three-component aerodynamic coefficients (Drag, Lift, and Pitching moment) of MoDKI were successfully measured at the angle of attack from 0.7 to 3.4 degrees under a Mach 8 free-stream test flow condition. A linear regression fitting revealed a 95% prediction interval as the measurement precision of each aerodynamic coefficient.read more
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References
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Journal ArticleDOI
Hypersonic aerothermodynamic and scramjet research using high enthalpy shock tunnel
TL;DR: The largest high enthalpy shock tunnel HIEST was built at NAL Kakuda in 1997, aiming for aerodynamic tests of Japan's space vehicle HOPE and scramjet propulsion systems as discussed by the authors.
Journal ArticleDOI
Experiments on supersonic combustion ramjet propulsion in a shock tunnel
TL;DR: In this paper, the axial force on the model was measured using a stress wave force balance, which is a recently developed technique for measuring forces in shock tunnels, and the results were found to compare satisfactorily with predictions based on established theoretical models, used with simplifying approximations.
Journal ArticleDOI
Improvement of a free piston driver for a high-enthalpy shock tunnel
Katsuhiro Itoh,S. Ueda,Tomoyuki Komuro,K. Sato,Mamoru Takahashi,Hiroshi Miyajima,Hideyuki Tanno,H. Muramoto +7 more
TL;DR: In this article, the authors proposed a simple piston/gas-dynamic model, and the tuned operation condition was formulated as an eigenvalue with which the piston has sufficiently high speed at the moment of diaphragm rupture, so as to maintain a constant driver gas pressure, and reduces its speed to come to rest when very closely approaching the end of the driver tube.
Journal ArticleDOI
Millisecond aerodynamic force measurement with side-jet model in theISL shock tunnel
TL;DR: In this paper, the authors present a measurement of the aerodynamic force produced by interaction of side jets and ambient flow and act on the surface of the model, and quantify the time necessary to establish quasistationary flow for the actual test conditions.